WO2008034214A1 - Buse d'inverseur de poussée pour une turbine à gaz de moteur à double flux - Google Patents

Buse d'inverseur de poussée pour une turbine à gaz de moteur à double flux Download PDF

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Publication number
WO2008034214A1
WO2008034214A1 PCT/CA2007/001531 CA2007001531W WO2008034214A1 WO 2008034214 A1 WO2008034214 A1 WO 2008034214A1 CA 2007001531 W CA2007001531 W CA 2007001531W WO 2008034214 A1 WO2008034214 A1 WO 2008034214A1
Authority
WO
WIPO (PCT)
Prior art keywords
thrust reverser
doors
door
nozzle
central axis
Prior art date
Application number
PCT/CA2007/001531
Other languages
English (en)
Inventor
Jean-Pierre Lair
Original Assignee
Pratt & Whitney Canada Corp.
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Pratt & Whitney Canada Corp. filed Critical Pratt & Whitney Canada Corp.
Priority to CA2660001A priority Critical patent/CA2660001C/fr
Publication of WO2008034214A1 publication Critical patent/WO2008034214A1/fr

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/56—Reversing jet main flow
    • F02K1/60—Reversing jet main flow by blocking the rearward discharge by means of pivoted eyelids or clamshells, e.g. target-type reversers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to a thrust reverser nozzle, and in particular to a thrust reverser nozzle for a turbofan gas turbine engine. It also relates to a method of providing aerodynamic braking of an aircraft.
  • aerodynamic decelerating means It is generally desired to assist wheel braking using aerodynamic decelerating means on aircrafts equipped with gas turbine engines because of the high landing speeds of these aircrafts.
  • the aerodynamic decelerating means are especially useful on wet or icy runways to enhance the stopping capability of aircrafts.
  • a thrust reverser nozzle is one example of aerodynamic decelerating means used on aircrafts with one or more turbofan gas turbine engines.
  • a thrust reverser nozzle deflects at least a portion of the air from the gas turbine engine to create a braking force slowing down the aircraft.
  • the deflected air can come from the by-pass flow or from both the by-pass flow and the core flow.
  • thrust reverser nozzles are generally satisfactory when they are in the deployed position, it is still desirable to further improve the design of the stowed configuration of the thrust reverser nozzles for turbofan gas turbine engines, so that the engines forward thrust performance is not affected by the presence of the thrust reverser nozzles.
  • the present concept provides a thrust reverser nozzle for a nacelle of a turbofan gas turbine engine, the nacelle having a central axis and a propulsive jet outlet, the thrust reverser nozzle comprising a first reverser door and a second reverser door defining a portion of an aft section of the nacelle, the doors having a respective trailing edge adjacent to the propulsive jet outlet and being asymmetrically pivotable between a stowed position and a deployed position, one of the doors having a pivot axis closer to the central axis of the nacelle than the other door.
  • the present concept provides a thrust reverser for a turbofan engine having a central axis of rotation and an exhaust nozzle, the thrust reverser comprising first and second deflectors pivotally attached to the engine such that the first deflector pivots about a single non-translating first pivot axis and the second deflector pivots about a single non-translating second pivot axis, the first and second pivot axes extending generally transverse to the central axis, the first and second deflectors pivoting between respective stowed and deflecting positions, the first and second pivot axes being asymmetrically radially spaced relative to the central axis.
  • the present concept provides a thrust reverser for a turbofan engine having a central axis of rotation, the thrust reverser comprising at least first and second deflectors having respective pivot axes, the pivot axes disposed at different radial distances from the central axis.
  • the present concept provides a method of providing aerodynamic braking of an aircraft using a turbofan gas turbine engine mounted in a nacelle, the nacelle generally defining a central axis, the method comprising: operating the engine; operating at least one actuator to pivot, from a stowed position to a deployed position, a first and a second door provided at a rear section of the nacelle, the first door pivoting around a first rotation axis and the second door pivoting around a second rotation axis, one among the first rotation axis and the second rotation axis being closer than the other to the central axis; and then increasing output thrust generated by the engine with the doors in their deployed position. Further details of these and other aspects of the improved thrust reverser nozzle will be apparent from the detailed description and figures included below.
  • FIG. 1 schematically shows a generic turbofan gas turbine engine to illustrate an example of a general environment around which the improved thrust reverser nozzle can be used;
  • FIG. 2A is a side view of an example of a nacelle without a thrust reverser nozzle
  • FIG. 2B is a side view of an example of a nacelle with the improved thrust reverser nozzle in a direct thrust position
  • FIG. 3 is a rear view of the nacelle shown in FIG. 2B;
  • FIG. 4 is a side view showing the interior of the aft section of the nacelle with the thrust reverser nozzle of FIG. 2B;
  • FIG. 5 is a view similar to FIG. 4, with the doors in the deployed position;
  • FIG. 6 is a view similar to FIG. 5, showing the thrust reverser nozzle with the fairings;
  • FIGS. 7A to 7E schematically show various configurations of the pivot axes with reference to the central axis of the nacelle
  • FIGS. 8A to 8E schematically show a variant of the different configurations for the pivot axes
  • FIG. 9 shows another example of an improved thrust reverser nozzle, with the doors in their stowed position
  • FIG. 10 is a perspective view showing the thrust reverser nozzle of FIG. 9 with the doors in their deployed position.
  • FIG. 11 is a view similar to FIG. 10, with the doors being removed.
  • FIG. 1 illustrates a turbofan gas turbine engine 10 of a type preferably provided for use in subsonic flight, generally comprising in serial flow communication a fan 12 through which ambient air is propelled, a multistage compressor 14 for pressurizing the air, a combustor 16 in which the compressed air is mixed with fuel and ignited for generating an annular stream of hot combustion gases, and a turbine section 18 for extracting energy from the combustion gases.
  • FIG. 1 only shows one example of the engine with which the improved thrust reverser nozzle can be used. The improved thrust reverser nozzle can also be used with other turbofan models.
  • FIG. 2A there is shown an example of a nacelle 20' without a thrust reverser nozzle.
  • the turbofan gas turbine engine is located within the nacelle and the nacelle is attached under the wings or on the fuselage of the aircraft using an appropriate arrangement (not shown).
  • FIG. 2B shows an example of a nacelle 20 with the improved thrust reverser nozzle 22.
  • the thrust reverser nozzle 22 is integrated within the outer and inner dimensions of the original nacelle so that the direct thrust performance of the engine is not affected.
  • the following key parameters of the nacelle exhaust i.e., the mixing length, throat location, exit shape of the exhaust, inner and outer flow contour, base area, etc. are the same as the nacelle 20' of FIG. 2A. This ensures that the performance of the engine will be the same in the direct thrust mode of operation when using the nacelle 20 instead of the original nacelle 20'.
  • the thrust reverser nozzle 22 is provided in the aft section 20a of the nacelle 20.
  • Each door 24, 26 has a trailing edge 24a, 26a adjacent to the propulsive jet outlet 28.
  • doors are described in the detailed description and shown in the drawings as being an upper reverser door and a bottom reverser door movable in a vertical plane, the doors can also be configured as a left door and right door movable in a horizontal plane.
  • FIG. 3 is a rear view of the nacelle 20 shown in FIG. 2B. This view shows the upper reverser door 24 and the bottom reverser door 26 in their stowed position.
  • the trailing edges 24a, 26a of both doors 24, 26 partially define the exhaust nozzle.
  • the exhaust nozzle is concentric with a central axis 32 of the nacelle 20.
  • the doors 24, 26 are separated on each side by a fairing 34 which covers a part of a door linkage system.
  • Each fairing 34 includes a hinged flap 35 that is described hereafter.
  • FIG. 4 there is shown the interior of the aft section 20a of the nacelle 20.
  • This figure shows the linkage system for moving the doors 24, 26 from their stowed position to a deployed position, and vice-versa.
  • the doors 24, 26 are connected, on each side, to a fixed structure around which a linking arm pivots.
  • the fixed structure is hereby referred to as the jet pipe 36.
  • the upper door 24 has a curved or L-shaped linking arm 38 pivoting around a substantially horizontal pivot axis 40 located slightly below the central axis 32.
  • FIG. 4 further illustrates the bottom door 26 being connected to a substantially straight linking arm 42 pivoting around a substantially horizontal pivot axis 44 located above the center axis 32.
  • the linking arms 42 of the bottom door 26 can also be L-shaped or have any other shape, in accordance with the design requirements.
  • the arms of both doors 24, 26 are connected to their respective door at a point that is upstream their pivot axis 40, 44. This is advantageous in terms of rigidity since the outer diameter of the doors 24, 26 is larger in the upstream direction. Both arms are also curved to follow and fit in the space defined by the inner and outer contours of the thrust reverser nozzle 22.
  • the arms 42 on both sides of the bottom door 26 are laterally offset with reference to the arms 38 of the upper door 24 so as to prevent them from colliding.
  • Each side of the thrust reverser nozzle 22 comprises a linear actuator 50 located between the two doors 24,26 and in substantially a horizontal plane that contains the center axis 32.
  • Each actuator 50 has two links 52, 54, one being connected to the upper reverser door 24 and the other to the bottom reverser door 26.
  • the linkage of the actuator 50 is asymmetrically connected to the doors 24, 26, as further explained hereafter.
  • FIG. 5 shows the trust reverser nozzle 22 of FIG. 4 with the doors 24, 26 in their deployed position.
  • the doors 24, 26 are asymmetrically pivoted form their stowed position to their deployed position.
  • the trailing edge 24a of the upper door 24 pivots into the bottom door 26.
  • the doors 24, 26 are pivoted up to an angle where the propulsive jet coming out of the engine is deflected by the doors 24, 26 and can generate a force which axial component provides the retarding force to the aircraft. Therefore, once the doors 24, 26 are in their deployed position, increasing the output thrust generated by the engine creates an aerodynamic decelerating force.
  • the linkage of the actuator 50 is asymmetrically connected to the doors 24, 26.
  • the door with the shortest hinge arm has the shortest link.
  • the jet pipe 36 comprises two side arms 36a extending towards their rear.
  • the doors 24, 26 are designed with complementary jet pipe portions 60, 62 attached to the reverser doors inner skin.
  • the complementary jet pipe portions 60, 62 fit into a corresponding recess on the jet pipe 36 to obtain substantially a complete jet pipe when the doors 24, 26 are in their stowed position. This way, when the doors 24, 26 are in their stowed position, the jet pipe 36 can be almost identical to the jet pipe within a nacelle that is not provided with the thrust reverser nozzle, such as the nacelle 20' of FIG. 2A.
  • the complementary jet pipe portion 60, or reverser door inner skin under the upper reverser door 24 can be longer to compensate the fact that the door 24 is closer to the jet pipe 36 when set in the deployed position.
  • the corresponding recess of the jet pipe 36 will then be modified accordingly, such as the extended recess 36a shown in stippled lines in FIG. 6. This participates in ensuring a good compatibility between the engine and the thrust reverser nozzle by controlling the spacing ratio, i.e., the distance between the door and the recess of the jet pipe 36.
  • the increased distance between the door and the exit plane of the jet pipe 36 will help maintaining the engine surge margin when the reverser nozzle 22 is deployed.
  • FIG. 6 is a view similar to FIG. 5, showing the fairing 34 and the hinged flap 35.
  • the aft of the hinged flap 35 is outwardly pivoted when the doors 24, 26 move from their stowed position to their deployed position.
  • the flap 35 moves outwards so as to make room to the longitudinal edge of the doors 24, 26.
  • the flaps 35 are biased towards the interior by a spring, for instance a leaf spring, but are pushed toward the outside when the doors 24, 26 are rotated.
  • FIGS. 7A to 7E show different embodiments for the relative position of the pivot axes with reference to the central axis of the nacelle 20.
  • one of the doors has a pivot axis closer to the central axis 32 of the nacelle 20 than the other door.
  • the pivot axis 44 of the bottom door 26 is above the central axis 32 of the nacelle 20 while the pivot axis 40 of the upper door 24 is below the central axis 32.
  • the pivot axis 40 of the upper door 24 is closer to the central axis 32 than the bottom door 26. Both pivoting axes lay in a common vertical plane.
  • FIG. 7B 1 the pivot axis 40 of the upper door 24 is in registry with the central axis 32.
  • FIG. 7C the pivot axis 40 of the upper door 24 is above the central axis 32. Both pivoting axes lay in a common vertical plane.
  • FIGS. 7D and 7E show variants that are applicable to either FIG. 7A, 7B or 7C. It shows that the pivot axis 44 of the bottom door 26 can be offset by a distance "d" that is either upstream or downstream with reference to the jet flow.
  • FIGS. 8A to 8E show alternative embodiments of the pivot axes.
  • the pivot axis 40 of the upper door 24 is above the central axis 32 while the pivot axis 44 of the bottom door 26 is slightly below the central axis 32.
  • the pivot axis 44 of the bottom door 26 is in registry with the central axis 32 of the nacelle 20.
  • the pivot axis 44 of the bottom door 26 is slightly above the central axis 32 of the nacelle 20. Both pivoting axes lay in a common vertical plane.
  • FIGS. 8D and 8E show the pivot axes being offset, either upstream or downstream. Again, this is applicable to either FIG. 8A, 8B or 8C.
  • FIG. 9 shows a variant of the thrust reverser nozzle 22.
  • the fairing 34 is fixed.
  • the flaps 70 form the rear portion of the jet pipe arms and of the continuation of the fairing 34.
  • Each flap 70 is pivotable with reference to a vertical axis substantially located at the forward end of the flap. The flaps pivot inward the reverser nozzle when the reverser doors 24, 26 are moved from their stowed to their deployed position and come back to their stowed position when the reverser doors move from their deployed to their stowed position.
  • FIG. 10 shows the doors 24, 26 in their deployed position.
  • FIG. 11 shows the deployed position of the thrust reverser nozzle 22, but without the doors.
  • the flaps 70 were allowed to pivot slightly inwards so as to provide room for the sides of the doors and also to concentrate the jet towards the center when the thrust reverser nozzle 22 is deployed.
  • the thrust reverser nozzle 22 has many advantages, including being a simple and robust construction that is foremost capable of duplicating the forward thrust performance of a nacelle that is not fitted with a thrust reverser. This is made possible because the thrust reverser installation does not substantially change the nacelle key design parameters such as nacelle length, base area, mixing length, throat location, inner and outer flow surfaces. When in its deployed position, the thrust reverser nozzle 22 is also capable of providing a retarding force to the aircraft during landing.
  • the asymmetrical pivoted doors have many advantages.
  • the actuator is located between the two reverser doors, as previously described.
  • a dedicated actuator per door can be installed in a substantially vertical plane that contains the reverser nozzle central axis.
  • each actuator is located in the plane of symmetry of each door, and each actuator controls the position of their dedicated reverser door.
  • One end of the actuator is pivotally mounted on the jet pipe while its other end, the piston rod is directly and pivotally mounted to the dedicated reverser door, thus eliminating the need of links 52 and 54 of FIGS. 4, 5.
  • thrust reverser nozzle of the invention can be considered for installation on new engines and nacelles as well as retro-fits. Still other modifications which fall within the scope of the present invention will be apparent to those skilled in the art, in light of a review of this disclosure, and such modifications are intended to fall within the appended claims.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Rolling Contact Bearings (AREA)

Abstract

invention concerne un inverseur de poussée comprenenant une première porte d'inverseur (24) et une seconde porte d'inverseur (26) qui peut pivoter de façon asymétrique entre une position arrimée et une position déployée, l'une étant dotée d'un axe de pivot plus proche de l'axe central (32) que l'autre.
PCT/CA2007/001531 2006-09-21 2007-08-29 Buse d'inverseur de poussée pour une turbine à gaz de moteur à double flux WO2008034214A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CA2660001A CA2660001C (fr) 2006-09-21 2007-08-29 Buse d'inverseur de poussee pour une turbine a gaz de moteur a double flux

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US11/534,202 2006-09-21
US11/534,202 US8015797B2 (en) 2006-09-21 2006-09-21 Thrust reverser nozzle for a turbofan gas turbine engine

Publications (1)

Publication Number Publication Date
WO2008034214A1 true WO2008034214A1 (fr) 2008-03-27

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PCT/CA2007/001531 WO2008034214A1 (fr) 2006-09-21 2007-08-29 Buse d'inverseur de poussée pour une turbine à gaz de moteur à double flux

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US (1) US8015797B2 (fr)
EP (1) EP1903205B1 (fr)
CA (1) CA2660001C (fr)
WO (1) WO2008034214A1 (fr)

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US20080072570A1 (en) 2008-03-27
CA2660001C (fr) 2012-06-12
EP1903205B1 (fr) 2015-10-14
EP1903205A2 (fr) 2008-03-26
US8015797B2 (en) 2011-09-13
EP1903205A3 (fr) 2011-04-13

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